A structural component, including a composite tapered wing spar having a web and two flanges on opposite sides of the web, the composite tapered wing spar having a first fiber layer made up of a plurality of plies, wherein the plies have respective longitudinal axes that are straight, wherein a first ply of the plurality of plies is effectively parallel to a respective direction of extension of one of the flanges at a first transition zone of the one flange and web, wherein a second ply of the plurality of plies is effectively parallel to a respective direction of extension of the other of the flanges at a second transition zone of the other flange and web, and wherein at least most plies of the plurality of plies of the first layer located between the first ply and the second ply extend at respective oblique angles relative to the respective directions of extensions of the first ply and the second ply.
LONGITUDINAL PLY LAYUP OF COMPOSITE SPAR
2016-02-11
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |